CFRP laminate delamination failure behavior prediction method based on novel cohesion constitutive relation

A constitutive relationship and prediction method technology, applied in the direction of applying stable tension/compression to test the strength of materials, analyzing materials, measuring devices, etc., can solve the problems of damage expansion design, lack of physical basis for assumptions, and no clear calculation methods, etc. Achieve the effects of reducing test costs, good accuracy and applicability, and shortening the workload of experimental testing

Inactive Publication Date: 2019-10-25
CHONGQING UNIV
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Problems solved by technology

The researchers proposed to adopt a cohesion model considering the influence of fiber bridging, but the assumptions in the construction of existing constitutive models lack physical basis
In addition, the determination of the model requires many parameters, and there is no clear calculation method for these parameters, which makes it difficult for the model to be used in the damage propagation design of actual composite material structures

Method used

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  • CFRP laminate delamination failure behavior prediction method based on novel cohesion constitutive relation
  • CFRP laminate delamination failure behavior prediction method based on novel cohesion constitutive relation
  • CFRP laminate delamination failure behavior prediction method based on novel cohesion constitutive relation

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Embodiment Construction

[0041] Below in conjunction with embodiment the present invention is described in further detail:

[0042] The specific implementation steps of a method for predicting the delamination failure behavior of CFRP laminates based on the new cohesive force constitutive relation of the present invention are as follows:

[0043] Step 1: Design and manufacture CFRP laminate delamination specimens with 0° / 5°, 45° / -45° and 90° / 90° according to ASTM D5528-13 standard. The sample is made of unidirectional prepreg of T700 / QY9511 carbon fiber / bismaleimide resin system, and the layup sequence is 0 16 / / (+5 / -5 / 0 6 ) S , (+45 / -45 / 0 6 ) S / / (-45 / +45 / 0 6 ) S and (90 / 0 / 90 / 0 5 ) S / / (90 / 0 / 90 / 0 5 ) S . The symbol / / indicates where the preformed cracks introduced during the manufacturing process are located. The size of the cut prepreg is 385mm×370mm. In the process of laying the prepreg, a layer of polytetrafluoroethylene layer with a thickness of 25 μm and a length of 35 mm is pre-lai...

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Abstract

The invention relates to a CFRP laminate delamination failure behavior prediction method based on a novel cohesion constitutive relation. The method comprises the following steps that (1) CFRP laminate delamination test pieces with different layinginterfaces are designed and manufactured; (2) a DCB device is adopted to carry out a delamination test; (3) interlamination fracture toughness is calculated through a corrected beam theory; (4) a CT scanning technology and an SEM technology are adopted to reveal a laminate delamination microscopic failure mechanism, and the novel cohesion constitutive relation based on the failure mechanism is established; (5) a key parameter model of the novel cohesion constitutive relation is established through a numerical method; (6) the correctness and applicability of the novel cohesion constitutive relation are verified; and (7) a cohesion model passing verification is adopted to predict a CFRP laminate delamination extension behavior under an arbitrary interface layer angle. Through the method, the delamination failure behavior of a typical CFRP laminate structure can be effectively predicted, the test cycle is remarkably shortened, and test costis lowered; and meanwhile, a theoretical basis is provided for integrated design of damage tolerance evaluation and material structural strength of a CFRP structural component.

Description

technical field [0001] The invention relates to a method for predicting the delamination failure behavior of CFRP laminates based on a new type of cohesive force constitutive relationship, which is suitable for the prediction of the delamination failure behavior and structural strength of CFRP laminates widely used in the fields of aerospace, wind power, rail transit and sports. . Background technique [0002] Composite materials with high specific strength and specific stiffness are widely used in modern aircraft to reduce structural weight and improve fuel efficiency. Laminates are one of the most commonly used configurations in aircraft composite structures, but due to the lack of reinforcement in the thickness direction, the interlaminar properties of composite laminates are much lower than their in-plane properties. At the same time, due to the mismatch of Poisson's ratio between plies and the anisotropy of thermal expansion coefficient, stress concentration areas betw...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01N3/08G06F17/50
CPCG01N3/08G01N2203/0216G06F30/23
Inventor 龚愉刘浩姚建尧张建宇胡宁
Owner CHONGQING UNIV
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